US Patent 7918644 Axial-flow compressor for a gas turbine engine

An axial-flow compressor for a gas turbine engine has a rotor drum (2) in thermally lower loaded first compressor stages (3 to 6) which includes a one-piece ring, or rotor rings (7 to 10) attached to one another. Fiber belts (18, 21) are wound onto these rings close to the rotor blades and include carbon fibers embedded in a high-temperature resistant polymer matrix. As the rotor disks can be dispensed with, since their function will be assumed by the fiber belts, the compressor features low weight, requires limited space only, and, in addition, can be produced cost-effectively.